def noise_flyover(nexus):
nexus.analyses.takeoff.noise.settings.flyover = True
nexus.analyses.takeoff.noise.settings.sideline = False
results = nexus.results
mission = nexus.missions.takeoff
results.flyover = mission.evaluate()
if nexus.save_data:
save_results(results.flyover, 'flyover.res')
else:
results.flyover = load_results('flyover.res')
noise_segment = results.flyover.segments.climb
noise_settings = nexus.analyses.takeoff.noise.settings
noise_config = nexus.vehicle_configurations.takeoff
noise_analyses = nexus.analyses.takeoff
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Flyover_climb.dat'
noise_config.output_file_engine = 'Noise_Flyover_climb_Engine.dat'
if nexus.npoints_takeoff_sign == -1:
noise_result_takeoff_FL_clb = 500. + nexus.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_FL_clb = compute_noise(noise_config,
noise_analyses,
noise_segment,
noise_settings)
noise_segment = results.flyover.segments.cutback
noise_settings = nexus.analyses.takeoff.noise.settings
noise_config = nexus.vehicle_configurations.cutback
noise_config.print_output = 1
noise_config.engine_flag = True
noise_config.output_file = 'Noise_Flyover_cutback.dat'
noise_config.output_file_engine = 'Noise_Flyover_cutback_Engine.dat'
if nexus.npoints_takeoff_sign == -1:
noise_result_takeoff_FL_cutback = 500. + nexus.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_FL_cutback = compute_noise(
noise_config, noise_analyses, noise_segment, noise_settings)
noise_result_takeoff_FL = 10. * np.log10(
10**(noise_result_takeoff_FL_clb / 10) +
10**(noise_result_takeoff_FL_cutback / 10))
nexus.summary.noise.flyover = noise_result_takeoff_FL
return nexus
def noise_approach(nexus):
nexus.analyses.landing.noise.settings.approach = True
results = nexus.results
mission = nexus.missions.landing
results.approach = mission.evaluate()
if nexus.save_data:
save_results(results.approach, 'approach.res')
else:
results.approach = load_results('approach.res')
noise_segment = results.approach.segments.descent
noise_analyses = nexus.analyses.landing
noise_settings = nexus.analyses.landing.noise.settings
noise_config = nexus.vehicle_configurations.landing
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Approach.dat'
noise_config.output_file_engine = 'Noise_Approach_Engine.dat'
noise_result_approach = compute_noise(noise_config, noise_analyses,
noise_segment, noise_settings)
nexus.summary.noise.approach = noise_result_approach
return nexus
def sideline_noise(analyses,noise_configs):
"""This method calculates sideline noise of a turbofan aircraft
Assumptions:
N/A
Source:
N/A
Inputs:
analyses - data structure of SUAVE analyses [None]
noise_configs - data structure for SUAVE vehicle configurations [None]
Outputs:
SPL - sound pressure level [dB]
Properties Used:
N/A
"""
# Update number of control points for noise
mission = analyses.missions.sideline_takeoff
sideline_initialization_results = mission.evaluate()
n_points = np.ceil(sideline_initialization_results.segments.climb.conditions.frames.inertial.time[-1] /0.5 +1)
mission.npoints_sideline_sign = np.sign(n_points)
mission.segments.climb.state.numerics.number_control_points = int(np.minimum(200, np.abs(n_points))[0])
# Set up analysis
noise_segment = mission.segments.climb
noise_segment.analyses.noise.settings.sideline = True
noise_segment.analyses.noise.settings.flyover = False
noise_analyses = noise_segment.analyses
noise_settings = noise_segment.analyses.noise.settings
noise_config = noise_configs.takeoff
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Sideline.dat'
noise_config.output_file_engine = 'Noise_Sideline_Engine.dat'
# Determine the x0
x0 = 0.
position_vector = noise_segment.conditions.frames.inertial.position_vector
degree = 3
coefs = np.polyfit(-position_vector[:,2],position_vector[:,0],degree)
for idx,coef in enumerate(coefs):
x0 += coef * 304.8 ** (degree-idx)
noise_segment.analyses.noise.settings.mic_x_position = x0
noise_config.engine_flag = True
if mission.npoints_sideline_sign == -1:
noise_result_takeoff_SL = 500. + noise_segment.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_SL = compute_noise(noise_config,noise_analyses,noise_segment,noise_settings)
return noise_result_takeoff_SL
def approach_noise(analyses, noise_configs):
"""This method calculates approach noise of a turbofan aircraft
Assumptions:
N/A
Source:
N/A
Inputs:
analyses - data structure of SUAVE analyses [None]
noise_configs - data structure for SUAVE vehicle configurations [None]
Outputs:
SPL - sound pressure level [dB]
Properties Used:
N/A
"""
# Update number of control points for noise
mission = analyses.missions.landing
approach_initialization = mission.evaluate()
n_points = np.ceil(approach_initialization.segments.descent.conditions.
frames.inertial.time[-1] / 0.5 + 1)
mission.npoints_takeoff_sign = np.sign(n_points)
mission.segments.descent.state.numerics.number_control_points = int(
np.minimum(200, np.abs(n_points))[0])
# Set up analysis
noise_segment = mission.segments.descent
noise_segment.analyses.noise.settings.approach = True
noise_analyses = noise_segment.analyses
noise_settings = noise_segment.analyses.noise.settings
noise_config = noise_configs.landing
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Approach.dat'
noise_config.output_file_engine = 'Noise_Approach_Engine.dat'
noise_result_approach = compute_noise(noise_config, noise_analyses,
noise_segment, noise_settings)
return noise_result_approach
def noise_sideline(nexus):
nexus.analyses.takeoff.noise.settings.sideline = True
nexus.analyses.takeoff.noise.settings.flyover = False
results = nexus.results
mission = nexus.missions.sideline_takeoff
results.sideline = mission.evaluate()
if nexus.save_data:
save_results(results.sideline, 'sideline.res')
else:
results.sideline = load_results('sideline.res')
# Determine the x0
x0 = 0.
position_vector = results.sideline.segments.climb.conditions.frames.inertial.position_vector
degree = 3
coefs = np.polyfit(-position_vector[:, 2], position_vector[:, 0], degree)
for idx, coef in enumerate(coefs):
x0 += coef * 304.8**(degree - idx)
nexus.analyses.takeoff.noise.settings.mic_x_position = x0
noise_segment = results.sideline.segments.climb
noise_settings = nexus.analyses.takeoff.noise.settings
noise_config = nexus.vehicle_configurations.takeoff
noise_analyses = nexus.analyses.takeoff
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Sideline.dat'
noise_config.output_file_engine = 'Noise_Sideline_Engine.dat'
if nexus.npoints_sideline_sign == -1:
noise_result_takeoff_SL = 500. + nexus.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_SL = compute_noise(noise_config, noise_analyses,
noise_segment, noise_settings)
nexus.summary.noise = Data()
nexus.summary.noise.sideline = noise_result_takeoff_SL
return nexus
def flyover_noise(analyses, noise_configs):
"""This method calculates flyover noise of a turbofan aircraft
Assumptions:
N/A
Source:
N/A
Inputs:
analyses - data structure of SUAVE analyses [None]
noise_configs - data structure for SUAVE vehicle configurations [None]
Outputs:
SPL - sound pressure level [dB]
Properties Used:
N/A
"""
# Update number of control points for noise
mission = analyses.missions.takeoff
takeoff_initialization = mission.evaluate()
n_points = np.ceil(takeoff_initialization.segments.climb.conditions.frames.
inertial.time[-1] / 0.5 + 1)
mission.npoints_takeoff_sign = np.sign(n_points)
mission.segments.climb.state.numerics.number_control_points = int(
np.minimum(200, np.abs(n_points))[0])
# Set up analysis
noise_segment = mission.segments.climb
noise_segment.analyses.noise.settings.sideline = False
noise_segment.analyses.noise.settings.flyover = True
noise_settings = noise_segment.analyses.noise.settings
noise_config = noise_configs.takeoff
noise_analyses = noise_segment.analyses
noise_config.engine_flag = True
noise_config.print_output = 0
noise_config.output_file = 'Noise_Flyover_climb.dat'
noise_config.output_file_engine = 'Noise_Flyover_climb_Engine.dat'
noise_config.engine_flag = True
if mission.npoints_takeoff_sign == -1:
noise_result_takeoff_FL_clb = 500. + noise_segment.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_FL_clb = compute_noise(noise_config,
noise_analyses,
noise_segment,
noise_settings)
noise_segment = mission.segments.cutback
noise_config = noise_configs.cutback
noise_config.print_output = 0
noise_config.engine_flag = True
noise_config.output_file = 'Noise_Flyover_cutback.dat'
noise_config.output_file_engine = 'Noise_Flyover_cutback_Engine.dat'
if mission.npoints_takeoff_sign == -1:
noise_result_takeoff_FL_cutback = 500. + noise_segment.missions.sideline_takeoff.segments.climb.state.numerics.number_control_points
else:
noise_result_takeoff_FL_cutback = compute_noise(
noise_config, noise_analyses, noise_segment, noise_settings)
noise_result_takeoff_FL = 10. * np.log10(
10**(noise_result_takeoff_FL_clb / 10) +
10**(noise_result_takeoff_FL_cutback / 10))
return noise_result_takeoff_FL